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Lunar Descent Trajectory Optimization

Lunar Descent Trajectory Optimization. February 12, 2009. Page 1. Goal: To minimize propellant used during Lunar descent. Trajectory conditions: Apolune at 110km Vary perilune from 15km to 5km Allow sufficient time for attitude changes

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Lunar Descent Trajectory Optimization

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  1. Lunar Descent Trajectory Optimization February 12, 2009 [Alex Whiteman] [Mission Ops] Page 1

  2. Goal: To minimize propellant used during Lunar descent • Trajectory conditions: • Apolune at 110km • Vary perilune from 15km to 5km • Allow sufficient time for attitude changes • Leave propellant and altitude margin to allow for hover and obstacle avoidance Page 2

  3. Propellant use for each trajectory • Conclusions: • Lowering perilune decreases propellant mass • Diminishing returns as perilune keeps decreasing Page 3

  4. Backup Slide 1 EOM’s Mass flow rate equation Thrust perpendicular to surface of Moon Thrust parallel to surface of Moon Isp = 295s (H2O2/Polyethylene) Page 4

  5. Backup Slide 2 MATLAB EOM Script Page 5

  6. Backup Slide 3 MATLAB EOM Script (cont.) Page 6

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